发明名称 |
CENTRIFUGAL COMPRESSOR DIFFUSER PASSAGE BOUNDARY LAYER CONTROL |
摘要 |
A centrifugal compressor diffuser (42) includes a plurality of diffuser flow passages (22) extending through an annular diffuser housing (20) and circumferentially bounded by diffuser vanes (23) and axially bounded by forward and aft walls (101, 100). A diffuser boundary layer bleed (96) for the passages may include boundary layer bleed apertures (106) or slots (130) disposed through the forward wall (101) and a downstream facing wall (142) canted at an acute cant angle to a downstream diffuser airflow direction (103) in the passages. Diffuser bleed flow (112) is bled from a diffuser boundary layer. Boundary layer bleed apertures can be located downstream of throat sections (28) of the flow passages near pressure sides of the vanes. A centrifugal compressor (18) may include the diffuser surrounding an annular centrifugal compressor impeller (32) and apparatus for flowing impeller bleed flow (102) from a radial clearance between an impeller tip (36) and a diffuser annular inlet (27) with diffuser bleed flow either mixed or separately to cool a turbine (16). |
申请公布号 |
WO2016057112(A1) |
申请公布日期 |
2016.04.14 |
申请号 |
WO2015US44673 |
申请日期 |
2015.08.11 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
PARKER, DAVID, VICKEY;SMYTHE, CAITLIN, JEANNE;WILSON, JAMES, RICHARD |
分类号 |
F01D9/04;F02C3/08;F02C6/08;F02C7/18;F04D27/02;F04D29/44;F04D29/68 |
主分类号 |
F01D9/04 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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